Combined speed brake, escape hatch and baggage access door for aircraft



June 28, 1960 LE ROY F. ENGLISH 2,942,813 COMBINED SPEED BRAKE, ESCAPEHATCH AND BAGGAGE ACCESS DOOR FOR AIRCRAFT Filed Feb. 14, 1958 5Sheets-Sheet 1 INVENTOR. LE ROY F. ENGLISH Agent June 28, 1960 LE ROY F.ENGLISH 2,942,813

COMBINED SPEED BRAKE, ESCAPE HATCH AND BAGGAGE ACCESS DOOR FOR AIRCRAFT5 Sheets-Sheet 2 Filed Feb. 14, 1958 INVENTOR. LE ROY F ENGLlSH Age'ntJune 28, 1960 LE ROY F. ENGLISH 2,942,813

- COMBINED SPEED BRAKE, ESCAPE HATCH AND BAGGAGE ACCESS DOOR FORAIRCRAFT Filed Feb. 14, 1958 3 Sheets-Sheet 3 INVENTQR. R Y ENGLISH Agem United States Patent Ofiice Le Roy F. English, Northridge, Calif.,assignor to Lockheed Aircraft Corporation, Burbank, Calif.

Filed Feb. 14, 1958, Ser. No. 715,283

11 Claims. (Cl. 244129) This invention relates to structure means forpermitting access toand from an aircraft interior and aircraft speedretarding means during flight, and more particularly, to a combinationunitary structural device capable of serving as an in-flight speed brakefor the aircraft, a personnel emergency escape chute and anon-ground'access door and ladder to the aircraft interior.

Modern day aircraft contain many contrivances, each of which isspecially required to achieve adesired object 'or result. Some of suchthat are known in the prior art are: an in-fiight speed brake, whichusually consists of a panel member, either perforate or imperforate,that is mechanically moved into the free air stream: around the outersurfaces of the aircraft to slow it down; a personnel escape hatch to beused for emergency exit from the aircraft when in-flight emergenciesarise; and, access doors and laddersto the interior of the aircraft forplacement or removal of baggage .or cargo when the-aircraft is on theground. Heretofore known aircraft were not 'of the nature. that requiredall of the devices listed; that v is, the speed brakewas'generallylirnited to high speed military aircraft, whereas thetypeof aircraft requiring ;or having a baggage or;cargo access door andladder were in the operational spectru m requiring or necessitating aspeed brake. As for the escape hatch,vsuch is applicable to both highspeedmilitary, type aircraft requiring a speed brake and the slower typecargo and/or personnel carrier types of aircraft utilizing an acess doorand ladder. However, in aircraft requiring a plurality 'of such devicesthere has usually been a plurality of separate operating mechanisms, onefor each device or structure and system,iculminating in a plurality ofcontrol or actuating systems and an, increase in the operational weightof the aircraft. 7

Accordingly, it is an object of this invention toprovide a unitarystructural device that can operate 7 as a speed brake, a personnelescape chute and an access'door ladder. It is a further objectof thisinvention to provide 'a combinedunitary structural device enablingareduction fin the number of operatingfmechanisms, structures andsystems-required.-

2,942,813 7 Patented June 28, 1960 brake, personnel emergency escapehatch: chute and access door with ladder foran aircraft that consists ofone operating mechanism, structure and system, .while yet containing allthe desirable features of each device.

- It is a still further object of this invention to provide a unitarystructural device in an aircraft for operating as an in-flight speedbrake, personnel emergency escape hatch chute or access door with ladderthat is unique in design and containing a simple integration with theaircraft fuselage while yet operable with a single operating mechanismand system.

Other objects and advantages will become apparent from the followingdescription taken in connection with the accompanying drawing showingone of the embodiments of the invention in which:

Figure 1 is an elevational view of an aircraft incorporating thecombined structure, with the air-craft on the ground and the doorstructure extended;

Figure 2 is a perspective view of the combined door structure;

Figure 3 is a partial cross-sectional view of the portion of theaircraft adjacent the combined door structure, and showing the doorstructure in extended position, including the actuation and linkagedetails for actuation thereof;

Figure -4 is a partial cross-sectional view through the longitudinalcenterline of the combined door structure when in a retracted position;

' Figure 5 is a cross-sectional view taken along line 5--5'of Figure 4;i 7

Figure 6 is a cross-sectional view taken along line 6-,-6 ofFigure 4; lf Figures7, and -8 are enlargements of thedetails in cross sectionshowing the sealing arrangements between the combined door structure andthe spring-loaded doors thereim'.

' Figure 9 isan enlargement of the details in cross section showing thesealing arrangement between the lateral sides of the combined doorstructure and the fuselage; Figure 10 is an enlargement of the detailsin cross section showing the sealing arrangement between the aft end ofthe combined door structure and the fuselage; an .7 r 4 Figure .11 is aviewtaken' along line Ila-11 of Figure 1.

Generally stated, one embodiment of the invention is practiced by aunitary door like structure that is extend able from the aircraftfuselage envelope proper, such structureincorporatingrthe features of aspeed brake for in-flight operation, a personnel escape hatch chute forinflight evacuation of personnel during in-flight operation emergencies,and an access door with ladder to the airf Another'object of thisinvention is toprovidea device 1 for operatingfasanin-flight speed brakeat any flight fspe'ed the is capable of while'having means limiting the;mar air pressureforces reaeting againstqtl e brake structure whenextended.

A still furtlier object of this'invention i'sto provide a -A stillfurther object of this invention is to' provide a device combining thefunctions of an in-flight speed craft fuselage interior when theaircraft is on the ground.

- Referring more particularly to the drawings Figure 1 shows thecombined doordikestructure 1 inrextended position from opening 2 inaircraft fuselage 3, and indicating the adjacent juxtaposition of theaft end of the combined structure 1 with the groundline'when theaircraftis sitting on the ground. For the structure 1 to operate-as anemergency escape passage chute and an access door ladder, it isnecessary for such to be located on the lowerportion of theaircraftfuselage 3. However, the longitudinal location thereof as shownin Figure *1 -is the preferred location in view of the type of aircraftdepicted as an example, it being understood-that other types of aircraftstructure 1 may have any other longitudinal location that is readilyaccessible to the baggage or cargo compartment and/or the passengercompartment.

Referring to-Figures 2and'3, the combined structure '1 comprises anouter surface member 4, which is shaped -to fit flush in the opening 2in fuselage 3 when ina rertracted position, theshape of the surfaceformed by member 4 conforming to the outer surface of fuselage 3. The

, inner surface is. formed by two areuate or bowed sheet members securedin fixed relation to outer surface member 4 by a plurality of transversestructural members 6, 7, 8 and 9, having fhmges 6a, 7a, 8a and 9a alongthe inboard ,sidesthereof, and. longitudinal structural members 10., 11,12,13,147 and. 15, with the assembly of structural. members-645- withouter surface. member. 4 and the areuate sheet. members, 5. being; bywelding, riveting, or any other appropriate seeming or fastening means.a V t The sheet members Scot/er only a portion of assembly ofstructuralmembers 6-15 as can be more clearly seen 7 in EigureZ, in thatthe. forward lateral edges are on' cam roller channels 21. Movement isaccomplished by a hydraulic actuator 24 having an actuator rod 25pivotally aflixed to aircraft fuselage 3 by a bracket'25a. The body ofactuator 24 is pivotally connected to the aircraft fuselage 3 by links26 and to the structure 1 by links 27. Referring to Figure 3 therelation of actuator 24 and 7 links 26, 27 with the structure l whenextended from the flange 9a andthe-aitlateral edges are on flange. 7a,while i the longitudinal edges of one'member 5. are connected to.longitudinal. structural. member 12 and to longitudinal structuralmember by an intermediate member 16, ,while the other member 5 isconnected to. longitudinal structural member 13 and-tolongitudinalstructural mernher 15 by an intermediate member 17.Thus,;with members 5 secured totheassembly in this manner there ispresented a shallow U-shaped chute orchannel surface upon which aperson. canslide out of the aircraft; on during in-flight emergencieswhen the combined. door like structure 1 is extended from the fuselage3. It is also to be noted. use. of the structure 1 in an emergencyescape application, in. that when the structure 1. is extended from. theaircraft, it. serves as. a substantial shield for the. person thereon.to preventhis escape. path from being interfered: with by the windblastof the. airflow on the external surface of fuselage. 3 as. he must. bepast the r transverse structural. mernbergliv before any suchlinterference can occur By that time'he will be. considerable distancebelow'the lower surface of fuselage. 3-. i it In order to preventexcessive air pressure forces against the-combined structure 1-- whenextended in flight, there 'areincluded. plurality of springloadedorbiased doors 18, 19 and Such p ermits a flow of airthrough the Istructure 1, thus'allowing the structure 1 to be extended 1 fromthe.aircraftv for operation as a speed brake. at any speed which theaircraft is capable of operating at, 'andyet keeping the total airpressure forces against the structure 1 within design. limits. The doors18 which are located. between. longitudinal structural memberslZ and13;.and transversestructural member pairs 7-8 and 8-9 each consists oftwo portions, with each of the portionspivoted, on hinges located: ontheir longitudinal sides so as to swing inwardly in a transversedirection, as in- "moved from the centerline of structural 1. Door 19 isalso of a unitary construction located between structural members 6-11-714 and pivots inwardly around alateral .extend'j g hinge atits forwardlateral edge, as is illusgrated in the phantom lines in Figures 2 and'4. I t

; :ilnasmuchas inner surface sheet members 5 do not com.- iv

pletely ;co ver{ the lateral distance between longitudinal jstructuralmembers 12 and 13,; the. lateral structural anernbersj, 7;, and 9provide. steps so that the structure can. also 'serye as an; accessdoorwith integral ladder fuselage 3 is shown in solid lines, .While therelationship between; thesevmembers; when structure 1 is; retractedfiush with the. fuselage is shown in phantom. lines. It is to be notedthat actuator rod 25 is retracted into actuator 24 whenstructure l isextended from the aircraft fuselage 3, while actuator rod 251's extendedfrom the hydraulic actuator 24 when the; structure 1 is retractedv inopening 2 and flush withthe aircraft fuselage 3. 7 It is to beunderstood that any'type of actuating means may be used for extendingstructure 1 from fuselage 3, with the hydraulic actuator 24 as beingshown merely signifying a desirable. type which is located inboard when.door structure 1 is retracted. and that moves to an out of the wayposition or location when door structure. 1. iseXtended.

' Figures 7 and. 8 show thedetails offdoon's 19 and 20 seating in theopenings-of the. outer surface member 4, which includes a Thiokol, orrubber gasket, sealing means 28 between the overlapping surfaces. of thedoor structure proper and the outer surface member 4 of structure 1.

spring, 29incorporated therewith forbiasing the door 19Jtowardf aclosed; positiong again it being understood that this is only one meansof biasing the doors closed and isnot intended to be exclusive. I r sFigure 9 shows'themetaltometal sealing arrangement along thelongitudinally extendingadjaeent sides of. fuselarge 3 and outer s urface'member. 4;w.hen the door structrue 1 is retracted Ar channel-like.member fill secured to the aircraft fuselage .3 isiimoverlappingiengagement with the adjacent surfaces of aircraftfuselage 3. and .outer. surface member 4. IFigure 10 shows the sealbetween theaft lateral edge of outer surfaceimember 4 and fuselage 3'which comprising an L-shaped. member 31 secured. to fuselage 3 andextendingforward to overlap dicated. by the phantom'lines in Figures 2and .5. The

the -joint between adjacent edges of. fuselage 3. andouter surfacemember 4. This .closure seal is. metal to metal-similar to that shown inFigure 9,. w

The forward lateral edge of door" structure-1 isjshaped to provide anadditional air passage 32 therethrougli when a door structure 1 isextended from the aircraft for ineflight operation as a, speed brake, ascan be'seen in Figure. 11. As indicated above, with the air passagesproviding for a 'maximumglimit of air pressurev loads onithestructure IproperQthe structure 1 canalbe extended" to serve as a when irisextended while jthe aircraft' on the ground.

furthermore thelack of lateral coverage between longitudintrl structural.members 12 and .13 by members 5 per.

miiflhreugh 'n s ses hendqors: '18,: 19 and gear open for-loadreductions-on 1 when extendedin fightas. a speed brake. 1

integral wf h e lon t d n u t ra -m be s, 110

andits-tare channels. 21 which .ride on rollers 1 n. m ed on o e br c e2 which a s cured idle; aircraft fuselage 3. The ,CQeflCfiOIl. betweenchannels 7 2:1 and. rollers .22 guides the. structure 1 duringactuationso thatit .a predetermined path dictated by" the speed brakeat: any speed of the aircraft'withinthe speed r.ange. the aircraft is.capablegof' operating in. It has. been the experience when using thistype of s rueme in actual 'fl sht smt t during flight, snfihef a r afisnmn trimmedextehsion of the strueture to serve as :3 spe d brake hasno'tlresultedin y fleleteriqusefiect for deterioration t of the 1 acondition; of; the I aircraft that existedpriorto extensionofthed otilcture 1.. a y

In operation the combined; structure l may be extended to: serve :as a.brake, whereupon any p essure lea s on the 'sn'uetuz wilt relievedbilaieflow hrbngh passage-342M 11? op nin empties loaded doors 1s, '19and 20. Should an in-flighbemersas equg' evae atipn piper-50mg} in thug.eraft thestructure extended; whichin nu he yd a i a m t fl .4 am cu erthe way i nd e acuation mass by s eened dropping from the aircraft bysliding-dnmthechute like channel, generated by' he arcuate or" sheet:meme bers 5, the structure 1 in turn serving as a windblast protectionfor the evacuating personnel until they have cleared the lower portionof the fuselage 3 aft of opening 2.

When the aircraft is on the ground, by having the door structure 1located adjacent or near the baggage stowage area of the aircraft, freeaccess to such can be had by extending the structure and ingress oregress can be accomplished by utilizing the steps generated by thetransverse structure members 6, 7, 8 and 9.

Thus it can be seen that I have combined three separate and individuallyfunctional devices into one combined structure requiring only oneoperating mechanism. A considerable reduction in the space and weightrequisites are accomplished over the use of three separate operablesystems.

While a particular embodiment of the invention has been illustrated anddescribed, it will be obvious to those skilled in the art that variouschanges and modifications may be made without departing from theinvention and it is intended to cover in the appended claims all suchchanges and modifications that come within the true spirit and scope ofthe invention.

What is claimed is:

1. In an aircraft having a fuselage with an opening therein, a door likestructure, means linking said door structure to the aircraft fuselage,actuating means connected to both the door structure and the aircraftfuselage for extending and retracting the door structure between aretracted position fitting flush with the fuselage opening and anextended position whereby the door structure extends externally of theexterior of the fuselage, said door structure having inner and outersurface members fixedly secured to opposite sides of a plurality oflateral structural members, said outer surface member shaped to conformas the continuation of the outer fuselage surface over the fuselageopening when the door structure is in the retracted position, said outersurface member serving as an aircraft speed brake when in the extendedposition during flight, said inner surface formed by two laterallyspaced members forming a shallow elongate slideway of concavecross-section thereby providing an in-fiight personnel emergency escapechute when the door structure is in extended position during flight, andthe portion of said lateral structural members between the laterallyspaced inner surface members serving as steps of an access ladder to thefuselage interior when the door structure is extended and when theaircraft is on the ground.

2. The device as claimed in claim 1 wherein the linking means betweenthe door structure and aircraft fuselage comprises a cam channel on eachside of the door structure, and roller means affixed to the fuselageadjacent opposite sides of said opening, said roller means registeringin the cam channels for guiding the direction of the door structure whenactuated for movement from one position to another.

3. A unitary door structure providing a combined speed brake, emergencypersonnel escape chute, and access door ladder for an aircraftcomprising; a plurality of lateral extending structural members, aplurality of longitudinal extending structural members, said lateral andlongitudinal structural members united to form a structural frame, anouter surface member having a plurality of openings therein, said outersurface member secured to cover one side of said structural frame andshaped to conform to the outer surface of an aircraft fuselage, a pairof inner surface members, said inner surface member secured to cover aportion of the inner side of the structural frame with a lateraldisplacement relative to each other to enable the portion of the lateralstructural members extending between the adjacent sides of the innersurface members to provide integral access door ladder steps, said innersurface members shaped to form a shallow elongate slideway of concavecross-section, said slideway providing an 6 emergency personnel escapechute, and air pressure relief means mounted in the outer surface memberopenings for preventing excessive air pressure loads on the unitarystructure when used as an aircraft speed brake.

4. A unitary structure assembly for an aircraft comprising a firstmember, said first member constituting a speed brake having a surface ofcurvature conforming to an aircraft fuselage, at least two secondmembers spaced from said first member, said second members constitutingan emergency personnel escape chute as a shallow elongate slideway ofconcave cross-section, and a plurality of integral structural memberslocated between and interconnecting said first and second memberstogether maintaining said first and second members in fixed relativepositions, at least some of said integral structural membersconstituting access door ladder steps.

5. A unitary structural assembly for aircraft comprising a first memberhaving a plurality of openings therein, said first member constituting aspeed brake having a surface of curvature conforming to an aircraftfuselage, at least two second members spaced from said first member,said second members constituting an emergency personnel escape chute as.a shallow elongate slideway of concave cross-section, and a pluralityof integral structural members located between and interconnecting saidfirst and second members together maintaining said first and secondmembers in fixed relative positions, at least some of said integralstructural members constituting access door ladde-r steps, and airpressure relief means mounted in the outer surface member openings forpreventing excess'of air pressure loads on the unitary structure'whenused as an aircraft speed brake. ,6. A device as claimed in claim 5wherein the air pres- 1 sure relief means comprises spring biased doorshingedly connnected contiguous to the openings in the first-mem- .ber I,j 1. .l-El

7. In an aircraft having a fuselage with an opening therein, anextendible unitary door-like structure assembly capable of fitting inthe opening in a retracted position flush with the fuselage exterior,means linking said assembly to the aircraft fuselage, actuating means,said actuating means operatively connected to both the assembly and theaircraft fuselage .to move the assembly to extend externally of thefuselage, said assembly comprising a first member, said first memberconstituting a speed brake having a surface of curvature conforming tothe aircraft fuselage, at least two second members spaced from saidfirst member, said second members constituting an emergency personnelescape chute as a shallow elongate slideway of concave cross-section,and a plurality of integral structural members located between andinterconnecting said first and second members together maintaining saidfirst and second members in fixed relative positions, some of saidintegral structural members constituting access door ladder steps.

8. In an aircraft having a fuselage with an opening therein, a unitarydoor like structure assembly fitting in the opening flush with thefuselage exterior, a cam channel on each of two opposite sides of theassembly, roller means affixed to the fuselage on each of two oppositesides of the fuselage opening, actuating means, said actuating meansoperatively connected .to both the assembly and aircraft fuselage tomove the assembly to extend externally of the fuselage, the direction ofmovement of the assembly during such extension being guided by thecoaction between said roller means and said cam channels, said assemblycomprising a first member, said first member constituting .a speed brakehaving a surface of curvature conforming to the aircraft fuselage, atleast two second members spaced from said first member, said secondmembers constituting an emergency personnel escape chute as a shallowelongate slideway of concave cross-section, and a plurality of integralstructural members located between and interconnecting said first andsecond members together maintaining said first and second members in'fixed relative positions, some of said integral structural membersconstituting access door ladder stepsf i 9. In an laircr-a-ft having afuselage with an opening therein, a unitary door like structure assemblyfitting in ,the opening flush with thefuselage exterior, a cam channelon each of two opposite sides of the assembly,

roller means aff xed to the fuselage on each of two op posite sides ofthe fuselage opening, actuating means, a

said actuatingmeans operatively connected to both the assembly andaircraft fuselage to move the assembly to extend externally of thefuselage, the direction of movement of the assembly during suchextension being guided by the coac-tion between said roller means andsaid eam channels, said assembly comprising a first member having aplurality of openings therein, said first member constituting a speedbrake having a surface of curvature conforming to the aircraft fuselage,at least two second members space from said first member, said secondmembers constituting an emergency personnel escape chute as a shallowelongate slideway of concave cross-section, and a plurality of integralstructural members, said first and second members maintained in fixedrelative positions by said integral structural members located betweenand interconnecting said first and second members together maintainingsaid first and second members in spaced 7 m provide a combined speedbrake and access 'door lad der comprising: a plurality of laterallyextending strucsome a structural members, said lateral and longitudinalstruc tural members united to form a cellular honeycomb strucw turalframe, an outer surface member having a plurality of openings therein,said outer surface member secured to and coveringflone side of saidstructural frame and shaped to conform to the. outer surface of theaircraft fuselage,'eaeh of said openings in the outer surface mem berlocated in alignment with oneof the cells of the structuralirame, andainpressnre relief means mounted in the outer surface member openingsfor preventing excessive air pressure loads on the, door structure whenused as an aircraftispeed brake, said lateralstructural membersproviding integral access door ladder steps when the door is open whilethe aircraft is on the ground.

.11. A device as claimed in claim 101 wherein the air pressure reliefmeans comprises spring biased doors hingedly connected contiguoustheopenings in' the outer surface member.

References Cited in the file of this patent UNITED- STATES PATENTS V THER- REFERENCES S li- No. 252.299,, Dornier (A.P.-.C-), published May25,1941 V p Flight- Magazine-a July 1- No. 66, Issue No.

2.375,?age137; j H V v 7 Ta m

